[Federal Register Volume 81, Number 133 (Tuesday, July 12, 2016)]
[Proposed Rules]
[Pages 45075-45079]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-16322]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-7426; Directorate Identifier 2015-NM-199-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain The Boeing Company Model 737-100, -200, and -200C series
airplanes. This proposed AD is intended to complete certain mandated
programs intended to support the airplane reaching its limit of
validity (LOV) of the engineering data that support the established
structural maintenance program. This proposed AD would require
repetitive detailed, high frequency eddy current (HFEC), and ultrasonic
inspections of the center section rear spar upper clevis lugs and
horizontal stabilizer rear spar upper lugs, as applicable, for any
cracking, and related investigative and corrective actions if
necessary. For certain airplanes, this proposed AD would require
replacement of the center section rear spar upper chord with a new part
and a serviceable center section assembly. This proposed AD would also
require repetitive HFEC and fluorescent dye penetrant inspections of
the center section for cracking of the front and rear spar upper clevis
lugs or horizontal stabilizer front and rear spar upper lugs, and
related investigative and corrective actions if necessary. We are
proposing this AD to detect and correct cracking in the rear spar upper
clevis lugs of the center section, and in the rear spar upper lugs of
the horizontal stabilizer which could result in the loss of structural
integrity and controllability of the airplane.
DATES: We must receive comments on this proposed AD by August 26, 2016.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Boeing
Commercial Airplanes, Attention: Data & Services Management, P. O. Box
3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544-5000,
extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7426.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for
[[Page 45076]]
and locating Docket No. FAA-2016-7426; or in person at the Docket
Management Facility between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket contains this proposed AD, the
regulatory evaluation, any comments received, and other information.
The street address for the Docket Office (phone: 800-647-5527) is in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Payman Soltani, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone:
562-627-5313; fax: 562-627-5210; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2016-7426;
Directorate Identifier 2015-NM-199-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
As described in FAA Advisory Circular 120-104 (http://www.faa.gov/documentLibrary/media/Advisory_Circular/120-104.pdf), several programs
have been developed to support initiatives that will ensure the
continued airworthiness of aging airplane structure. The last element
of those initiatives is the requirement to establish a LOV of the
engineering data that support the structural maintenance program under
14 CFR 26.21. This proposed AD is the result of an assessment of the
previously established programs by the DAH during the process of
establishing the LOV for the affected airplanes. The actions specified
in this proposed AD are necessary to complete certain programs to
ensure the continued airworthiness of aging airplane structure and to
support an airplane reaching its LOV.
This proposed AD is intended to complete certain mandated programs
intended to support the airplane reaching its LOV of the engineering
data that support the established structural maintenance program. An
operator detected a cracked center section at the rear spar upper chord
clevis lug. This condition, if not corrected, could result in cracking
in the rear spar clevis lugs of the horizontal stabilizer center
section, which could result in loss of structural integrity and
controllability of the airplane.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-55A1033, Revision 2,
dated August 7, 2015. The service information describes procedures for
repetitive detailed, HFEC, and ultrasonic inspections of the center
section rear spar upper clevis lugs and rear spar upper lugs of the
horizontal stabilizer; HFEC and fluorescent dye penetrant inspections
for cracking in the front and rear spar upper clevis lugs of the center
section and the front and rear spar upper lugs of the horizontal
stabilizer. For certain airplanes, the service information describes
procedures for replacement of the center section rear spar upper chord
with a new part and replacing the center section with a serviceable
center section assembly, or installing bushings and sleeves as
applicable. This service information is reasonably available because
the interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in the service information described previously, except as discussed
under ``Differences Between This Proposed AD and the Service
Information.'' For information on the procedures and compliance times,
see this service information at http://www.regulations.gov by searching
for and locating Docket No. FAA-2016-7426.
The phrase ``related investigative actions'' is used in this NPRM.
Related investigative actions are follow-on actions that (1) are
related to the primary action, and (2) further investigate the nature
of any condition found. Related investigative actions in an AD could
include, for example, inspections.
The phrase ``corrective actions'' is also used in this NPRM.
Corrective actions are actions that correct or address any condition
found. Corrective actions in an AD could include, for example, repairs.
Differences Between This Proposed AD and the Service Information
Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August
7, 2015, specifies to contact the manufacturer for certain
instructions, but this proposed AD would require accomplishment of
repair methods, modification deviations, and alteration deviations in
one of the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
Where Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated
August 7, 2015, specifies a compliance time or repeat interval as
``Horizontal Stabilizer Center Section flight cycles'' or ``Horizontal
Stabilizer flight cycles,'' this AD requires compliance for the
corresponding time or repeat interval in airplane flight cycles.
Costs of Compliance
We estimate that this proposed AD affects 84 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts Cost on U.S.
Action Labor cost cost Cost per product operators
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Repetitive detailed, HFEC, and 9 work-hours x $85 $0 $765 per inspection $64,260 per
ultrasonic inspections. per hour = $765 per cycle. inspection cycle.
inspection cycle.
[[Page 45077]]
Repetitive HFEC and fluorescent 118 work-hours x $85 0 $10,030 per $842,520 per
dye penetrant inspections. per hour = $10,030 inspection cycle. inspection cycle.
per inspection cycle.
Replacement....................... Up to 252 25,000 Up to $46,420 per Up to $3,899,280 per
work[dash]hours x inspection cycle. inspection cycle.
$85 per hour =
$21,420 per
inspection cycle.
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We estimate the following costs to do any necessary inspections,
repairs, and replacements that would be required based on the results
of the proposed inspection. We have no way of determining the number of
aircraft that might need these inspections, repairs, and replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
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Bolt and Bushing Removal/ 101 work-hours x $85 $0 $8,585.
Inspection, Fabrication, and per hour = $8,585.
Installation.
Repair and replacement............. Up to 252 25,000 Up to $46,420 per inspection cycle.
work[dash]hours x
$85 per hour =
$21,420 per
inspection cycle.
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
The Boeing Company: Docket No. FAA-2016-7426; Directorate Identifier
2015-NM-199-AD.
(a) Comments Due Date
We must receive comments by August 26, 2016.
(b) Affected ADs
This AD affects AD 84-23-05, Amendment 39-4949 (49 FR 45744,
November 20, 1984); and AD 86-12-05, Amendment 39-5321 (51 FR 18771,
May 22, 1986).
(c) Applicability
This AD applies to The Boeing Company Model 737-100, -200, and -
200C series airplanes, certificated in any category, as identified
in Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated
August 7, 2015.
(d) Subject
Air Transport Association (ATA) of America Code 55, Stabilizers.
(e) Unsafe Condition
This proposed AD is intended to complete certain mandated
programs intended to support the airplane reaching its limit of
validity (LOV) of the engineering data that support the established
structural maintenance program. We are issuing this AD to detect and
correct cracking in the rear spar upper clevis lugs of the center
section, and in the rear spar upper lugs of the horizontal
stabilizer which could result in the loss of structural integrity
and controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections, Related Investigative and Corrective Actions (Service
Information Tables 1 and 3)
At the applicable time specified in table 1 or table 3 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-55A1033, Revision 2, dated August 7, 2015, except as specified
in paragraph (o) of this AD: Do detailed, high frequency eddy
current (HFEC), and ultrasonic inspections of the center section
rear spar upper clevis lugs for any cracking, and do all applicable
related investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
55A1033, Revision 2, dated August 7, 2015; except as specified in
paragraph (p) of this AD. Do all related investigative and
corrective actions before further flight. Repeat the inspections
thereafter at the applicable times specified in table 1 or table 3
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-55A1033, Revision 2, dated August 7, 2015.
(h) Replacement (Service Information Table 1)
For airplanes identified as Group 1, Configuration 1, in Boeing
Alert Service
[[Page 45078]]
Bulletin 737-55A1033, Revision 2, dated August 7, 2015: At the
applicable time specified in table 1 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033,
Revision 2, dated August 7, 2015, except as specified in paragraph
(o) of this AD, replace the center section rear upper chord with a
new part or replace the center section with a serviceable center
section assembly, in accordance with the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated
August 7, 2015.
(i) Repetitive Post-Replacement Inspections, Related Investigative and
Corrective Actions (Service Information Table 2)
For airplanes identified as Group 1, Configuration 1, in Boeing
Alert Service Bulletin 737-55A1033, Revision 2, dated August 7,
2015, with a new or serviceable 0.932-inch-thick center section rear
spar upper chord: At the applicable time specified in table 2 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-55A1033, Revision 2, dated August 7, 2015, except as specified
in paragraph (o) of this AD, do detailed, HFEC, and ultrasonic
inspections of the center section rear spar upper chord clevis lugs
for any cracking, and do all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-55A1033, Revision
2, dated August 7, 2015; except as specified in paragraph (p) of
this AD. Do all related investigative and corrective actions before
further flight. Repeat the inspections thereafter at the applicable
times specified in table 2 of paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August
7, 2015.
(j) Post-Replacement Inspections, Related Investigative and Corrective
Actions (Service Information Table 4)
For airplanes on which the center section rear spar upper chord
was last replaced with a new part or serviceable part: Within the
applicable times specified in table 4 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033,
Revision 2, dated August 7, 2015, except as specified in paragraph
(o) of this AD, do detailed, HFEC, and ultrasonic inspections of the
center section rear spar upper chord clevis lugs for any cracking,
and do all applicable related investigative and corrective actions,
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015;
except as specified in paragraph (p) of this AD. Do all related
investigative and corrective actions before further flight. Repeat
the inspections thereafter at the applicable times specified in
table 4 of 1.E., ``Compliance'' of Boeing Alert Service Bulletin
737-55A1033, Revision 2, dated August 7, 2015.
(k) Repetitive Inspections, Related Investigative and Corrective
Actions of the Horizontal Stabilizer (Service Information Table 5)
Within the applicable time specified in table 5 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033,
Revision 2, dated August 7, 2015, except as specified in paragraph
(o) of this AD, do detailed, HFEC, and ultrasonic inspections of the
rear spar upper lugs of the horizontal stabilizer for any cracking,
and do all applicable related investigative and corrective actions,
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015;
except as specified in paragraph (p) of this AD. Do all related
investigative and corrective actions before further flight. Repeat
the inspections thereafter at the applicable times specified in
table 5 of 1.E., ``Compliance'' of Boeing Alert Service Bulletin
737-55A1033, Revision 2, dated August 7, 2015.
(l) Post Replacement Inspections, Related Investigative and Corrective
Actions (Service Information Table 6)
For airplanes with a replaced horizontal stabilizer with a new
or serviceable part, within the applicable times specified in table
6 of 1.E., ``Compliance'' of Boeing Alert Service Bulletin 737-
55A1033, Revision 2, dated August 7, 2015, except as specified in
paragraph (o) of this AD: Do a detailed, HFEC, and ultrasonic
inspection of the rear spar upper lugs of the horizontal stabilizer
for any cracking, and do all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-55A1033, Revision
2, dated August 7, 2015; except as specified in paragraph (p) of
this AD. Do all related investigative and corrective actions before
further flight. Repeat the inspections thereafter at the applicable
times specified in table 6 of 1.E., ``Compliance'' of Boeing Alert
Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015.
(m) Scheduled Inspections, Related Investigative and Corrective Actions
(Service Information Table 7)
Within the applicable times specified in table 7 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033,
Revision 2, dated August 7, 2015, except as specified in paragraph
(o) of this AD: Do HFEC and fluorescent dye penetrant inspections
for cracking in the front and rear spar upper clevis lugs of the
center section and front and rear spar upper lugs of the horizontal
stabilizer, and do all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-55A1033, Revision
2, dated August 7, 2015; except as specified in paragraph (p) of
this AD. Do all related investigative and corrective actions before
further flight. Repeat the inspections thereafter at the applicable
times specified in table 7 of paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August
7, 2015.
(n) Post Scheduled Inspections, Related Investigative and Corrective
Actions (Service Information Table 8)
For airplanes on which the center section rear spar upper chord
or horizontal stabilizer rear spar upper chord has been replaced:
Within the applicable time specified in table 8 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033,
Revision 2, dated August 7, 2015, except as specified in paragraph
(o) of this AD: Do HFEC and fluorescent dye penetrant inspections
for cracking in the front and rear spar upper clevis lugs of the
center section or front and rear spar upper lugs of the horizontal
stabilizer, as applicable, and do all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
55A1033, Revision 2, dated August 7, 2015; except as specified in
paragraph (p) of this AD. Do all related investigative and
corrective actions before further flight. Repeat the inspections
thereafter at the applicable times specified in table 8 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033,
Revision 2, dated August 7, 2015.
(o) Exceptions to the Service Information: Compliance Times
(1) Where Boeing Alert Service Bulletin 737-55A1033, Revision 2,
dated August 7, 2015, specifies a compliance time ``after the
Revision 2 date of this service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(2) Where Boeing Alert Service Bulletin 737-55A1033, Revision 2,
dated August 7, 2015, specifies a compliance time or repeat interval
as ``Horizontal Stabilizer Center Section flight cycles'' or
``Horizontal Stabilizer flight cycles,'' this AD requires compliance
for the corresponding time or repeat interval in airplane flight
cycles.
(p) Exception to the Service Information: Repair Compliance Method
If any cracking of the lug is found during any inspection
required by this AD, and Boeing Alert Service Bulletin 737-55A1033,
Revision 2, dated August 7, 2015, specifies to contact Boeing for
appropriate action: Before further flight, repair the lug using a
method approved in accordance with the procedures specified in
paragraph (r) of this AD.
(q) Terminating Actions
(1) For Model 737-100, -200, and -200C series airplanes:
Accomplishment of the inspections specified in paragraph (g) of this
AD terminates the requirements of paragraph A. of AD 84-23-05,
Amendment 39-4949 (49 FR 45744, November 20, 1984).
(2) For Model 737-200 and -200C series airplanes: Accomplishment
of the inspections specified in paragraph (m) and (n) of this AD
terminates the requirements of paragraphs A. and B. of AD 86-12-05,
Amendment 39-5321 (51 FR 18771, May 22, 1986).
(r) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles Aircraft Certification Office
(ACO), FAA, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19. In accordance
with 14 CFR 39.19, send your request to your principal inspector or
local Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
[[Page 45079]]
attention of the person identified in paragraph (s)(1) of this AD.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Los Angeles ACO, to make those findings. To be approved,
the repair method, modification deviation, or alteration deviation
must meet the certification basis of the airplane and the approval
must specifically refer to this AD.
(s) Related Information
(1) For more information about this AD, contact Payman Soltani,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5313; fax: 562-627-5210; email: [email protected].
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544-
5000, extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on June 28, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-16322 Filed 7-11-16; 8:45 am]
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